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    Analysis of Composite Panels Subjected to Thermo-Mechanical Loads

    Source: Journal of Aerospace Engineering:;1999:;Volume ( 012 ):;issue: 001
    Author:
    Ahmed K. Noor
    ,
    Jeanne M. Peters
    DOI: 10.1061/(ASCE)0893-1321(1999)12:1(1)
    Publisher: American Society of Civil Engineers
    Abstract: The results of a detailed study of the effect of cutout on the nonlinear response of curved unstiffened panels are presented. The panels are subjected to combined temperature gradient through-the-thickness combined with pressure loading and edge shortening or edge shear. The analysis is based on a first-order, shear-deformation, Sanders-Budiansky-type shell theory with the effects of large displacements, moderate rotations, transverse shear deformation, and laminated anisotropic material behavior included. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the panel. The nonlinear displacements, strain energy, principal strains, transverse shear stresses, transverse shear strain energy density, and their hierarchical sensitivity coefficients are evaluated. The hierarchical sensitivity coefficients measure the sensitivity of the nonlinear response to variations in the panel parameters, as well as in the material properties of the individual layers. Numerical results are presented for cylindrical panels and show the effects of variations in the loading and the size of the cutout on the global and local response quantities as well as their sensitivity to changes in the various panel, layer, and micromechanical parameters.
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      Analysis of Composite Panels Subjected to Thermo-Mechanical Loads

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    http://yetl.yabesh.ir/yetl1/handle/yetl/44888
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    contributor authorAhmed K. Noor
    contributor authorJeanne M. Peters
    date accessioned2017-05-08T21:15:58Z
    date available2017-05-08T21:15:58Z
    date copyrightJanuary 1999
    date issued1999
    identifier other%28asce%290893-1321%281999%2912%3A1%281%29.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/44888
    description abstractThe results of a detailed study of the effect of cutout on the nonlinear response of curved unstiffened panels are presented. The panels are subjected to combined temperature gradient through-the-thickness combined with pressure loading and edge shortening or edge shear. The analysis is based on a first-order, shear-deformation, Sanders-Budiansky-type shell theory with the effects of large displacements, moderate rotations, transverse shear deformation, and laminated anisotropic material behavior included. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the panel. The nonlinear displacements, strain energy, principal strains, transverse shear stresses, transverse shear strain energy density, and their hierarchical sensitivity coefficients are evaluated. The hierarchical sensitivity coefficients measure the sensitivity of the nonlinear response to variations in the panel parameters, as well as in the material properties of the individual layers. Numerical results are presented for cylindrical panels and show the effects of variations in the loading and the size of the cutout on the global and local response quantities as well as their sensitivity to changes in the various panel, layer, and micromechanical parameters.
    publisherAmerican Society of Civil Engineers
    titleAnalysis of Composite Panels Subjected to Thermo-Mechanical Loads
    typeJournal Paper
    journal volume12
    journal issue1
    journal titleJournal of Aerospace Engineering
    identifier doi10.1061/(ASCE)0893-1321(1999)12:1(1)
    treeJournal of Aerospace Engineering:;1999:;Volume ( 012 ):;issue: 001
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
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